Various embodiments of the present technology may comprise a method and apparatus for a space-saving suspension system. In various embodiments, the apparatus may comprise a fine suspension device, a coarse suspension device, and a mechanical assembly. In various embodiments, the fine suspension device is arranged at an angle greater than zero degrees from the z-axis. In various embodiments, the mechanical assembly is coupled to the fine suspension device and a payload, such that when a force is exerted on the mechanical assembly by the payload, an applied force is transmitted to the fine suspension device.

Disclosed is a high altitude space launcher system for transferring payloads from surface to orbit at a significantly lower cost than conventional rockets. It comprises a aerostat lifted one stage light gas gun operating in stratosphere that shoots rocket assisted projectiles containing payload at near orbital velocities to a low angle trajectory. Alternatively, to launch acceleration sensitive payloads such as astronauts the light gas gun is replaced with a muzzle loaded conventional gun that shoots a single stage rocket at a much lower velocity. The system is mostly static structure, attached to a tether-elevator that moors it to land or a ship and provided it with electricity and lifts the projectiles to the gun.

A gun mounting lock and a method of using the same to secure a gun to a support surface. The gun mounting lock includes first and second arms positioned opposite each other and a ratchet assembly positioned between lower ends of the arms. The ratchet assembly engages gears provided on the lower ends of the arms. When the assembly is pushed downwardly by placing part of a gun thereon, the downward movement of the assembly causes the two arms to pivot towards each other simultaneously, capturing the gun between the arms and the assembly. The assembly is locked against movement in the reverse direction by a pin of a solenoid contacting a toothed flange on one of the arms. The assembly can be unlocked using a key or by providing power to the solenoid. The gun mounting lock housing is adjustably engaged with a track mounted on the support surface.

Consistent with various embodiments, a firearm securing apparatus has a first securing interface that is configured to generate a holding force between the apparatus and a support surface in response to an applied pressure. A second securing interface is configured and arranged to receive and secure a firearm barrel and includes a graspable feature. A support piece is configured and arranged to physically connect the two securing interfaces and to provide space, to allow a person's fingers to seize a graspable feature and to allow the person to apply pressure sufficient to overcome the holding force between the apparatus and the surface in order to remove the firearm from the apparatus when desired.

A magnetic shield for a locking device such as a gunlock having a first portion and a second portion configured for controlled movement with respect to the other portion and for being held in a fixed and locked position vis--vis each other. At least one of the first and second portions includes an electromechanical locking mechanism including a solenoid and solenoid activated spring loaded pin configured, in a first position, for preventing the first and second portions from moving with respect one another and in a second position for allowing the first and second portions to move vis--vis one another. A magnetically conducive shield is disposed on or in at least one of the first and second portion that includes the solenoid locking mechanism, for preventing an unauthorized magnetic field from causing the solenoid to retract the spring loaded pin thereby allowing the locking device to be opened.

A recoil management system.

A magnetic shield for a locking device such as a gunlock having a first portion and a second portion configured for controlled movement with respect to the other portion and for being held in a fixed and locked position vis--vis each other. At least one of the first and second portions includes an electromechanical locking mechanism including a solenoid and solenoid activated spring loaded pin configured, in a first position, for preventing the first and second portions from moving with respect one another and in a second position for allowing the first and second portions to move vis--vis one another. A magnetically conducive shield is disposed on or in at least one of the first and second portion that includes the solenoid locking mechanism, for preventing an unauthorized magnetic field from causing the solenoid to retract the spring loaded pin thereby allowing the locking device to be opened.

Various embodiments of the present technology may comprise a method and apparatus for a space-saving suspension system. In various embodiments, the apparatus may comprise a fine suspension device, a coarse suspension device, and a mechanical assembly. In various embodiments, the fine suspension device is arranged at an angle greater than zero degrees from the z-axis. In various embodiments, the mechanical assembly is coupled to the fine suspension device and a payload, such that when a force is exerted on the mechanical assembly by the payload, an applied force is transmitted to the fine suspension device.

A mounting system is provided including a center platform having a plurality of mounting lugs for mounting the center platform transversely extending at least partially through an aircraft cabin with a first end and second end of the center platform adjacent a respective first and second side opening of the aircraft cabin. A first support pylon may be removably coupleable to the first end of the center platform to extend outwardly from a first side of the aircraft. A second support pylon may be removably coupleable to the second end of the center platform to extend outwardly form a second side of the aircraft. A modular floor component may be removably coupleable relative to a longitudinal side of the center platform to provide a substantially planar load surface including a top portion of the modular floor component and a top surface of the center platform.

A mounting system is provided including a center platform having a plurality of mounting lugs for mounting the center platform transversely extending at least partially through an aircraft cabin with a first end and second end of the center platform adjacent a respective first and second side opening of the aircraft cabin. A first support pylon may be removably coupleable to the first end of the center platform to extend outwardly from a first side of the aircraft. A second support pylon may be removably coupleable to the second end of the center platform to extend outwardly form a second side of the aircraft. A modular floor component may be removably coupleable relative to a longitudinal side of the center platform to provide a substantially planar load surface including a top portion of the modular floor component and a top surface of the center platform.